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Arboga Robotmuseum

RB 04E

Robothistoriska Föreningen i Arboga

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Sidan uppdaterad: 2014-04-08 18:08

Start

Missile

Engine

Radar

Simulator

 

Missile History

 

V-1 bomb

 

Navy Experimental missiles

 

Air Force test missiles

 

Saab Experimental missiles

 

Air-to-surface missiles

 

Ship-to-ship missiles

 

Coastal missiles

  

Surface-to-air missiles

 

Anti-tank missiles

 

Target missiles

 

Submunition dispenser

 

Missile summary table

 

 

RB 04E

 

The Royal Swedish Air Force Materiel Administration mandated SAAB to upgrade the missile the RB 04 D to RB 04 E standard. In the technical specification it is stated that the missile should be used on the aircraft A 37 Thunderbolt and that the missile should be given an increased serviceability and interference stability. These requests resulted in the replacement of several units of the more modern version but with the same function as for the RB 04 D.

 

Function

The missile was propelled by a powder rocket motor. After launching at a high altitude the powder rocket ignited. The radar altimeter lowered the missile to about 30 feet (10 m) above the water level; subsequently the homing device started up. The homing unit was active mono- pulse radar homing, working with a frequency agile technique. The radar altimeter consisted of a transmitter- and a receiving unit and was placed in segregated areas of the missile.

 

The homing unit stabilized the missile attitude in pitch, yaw and roll, as the missile received impulses from the altimeter and the homing unit. Pneumatic signals were transmitted from the missile pilot to the servomotors for the control surfaces. The rudders for yaw and pitch were located at the front of the missile and the ailerons were situated at the trailing end of the wing.

 

RB 04 E became operational in 1975.

 

Steering control boxes

Pneumatic steering box (SAAB)

Pneumatic rudder servo (SAAB)

Radar altimeter unit (Philips)

Active radar homing unit (Philips)

 

Data

Imperial Units

Metric Units

Length

14

feet

7

inches

4 453

mm

Diameter

1

foot

8

inches

500

mm

Wing span

6

feet

5

inches

1 944

mm

Weight

1,375

lbs

 

 

625

kg

Rocket motor

KR 16 D2

 

 

 

 

 

Thrust

430

lbs

during 65.6 sec

 

1 913

N during 65,6 s

 

After launching at a high altitude the powder rocket ignited. The radar altimeter brought down the missile to about 30 feet (10 m) above the water level; subsequently the homing device started up. The homing unit was a single plane, active radar homing, working with a CW-mode. (Continuous  Wave-mode). With the assistance of the homing unit the missile was directed to above the target and the warhead was initiated by the proximity fuse.

 

 

 

Missiles type:

 

RB 04C

 

RB 04D

 

RB 04E

 

RB 05A

 

RB 05B/C

 

RB 75 Maverick

 

RB 15F